CN116310220A - Geometric surface reconstruction method for radiation temperature measurement area of turbine blade - Google Patents
Geometric surface reconstruction method for radiation temperature measurement area of turbine blade Download PDFInfo
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Abstract
A geometrical surface reconstruction method for a radiation temperature measurement area of a turbine blade is based on Comsol Multiphysics simulation software, belongs to the technical field of radiation temperature measurement of the turbine blade, and is characterized by comprising the steps of configuring a simulation environment, importing a geometrical model, configuring a geometrical optical physical field interface, dividing grids, configuring a solver, calculating, then deriving ray track coordinates, performing transformation under a space rectangular coordinate system on the three-dimensional coordinates by Matlab, performing geometrical reconstruction and mapping corresponding radiation temperature values, and is favorable for realizing the geometrical surface reconstruction of the radiation temperature measurement area, and particularly suitable for the temperature field reconstruction of the turbine blade.
Description
Technical Field
The invention belongs to the technical field of turbine blade radiation temperature measurement, and particularly relates to a geometric surface reconstruction method of a turbine blade radiation temperature measurement area.
Background
Turbine blades have a harsh operating environment, and generally adopt a radiation temperature measurement method to obtain surface temperature parameters. The common commercial or in-research pyrometer at present adopts a scanning single-point temperature measurement structure, and the temperature areas measured on the surface of the turbine blade are spliced and reconstructed through different installation positions, so that the temperature distribution of the whole blade surface is obtained; such scanning pyrometers often employ complex mechanical actuators to match the angular parameters of the mirror. The multi-point temperature measurement structure only adopts a fixed reflecting mirror to convert the light path, so that the complexity of the system can be effectively reduced, however, because of the limited installation environment in the turbine, the mode has higher requirements on the arrangement, encapsulation and the like of the multi-point probes; for smaller turbine blades, if multiple temperature measurement targets can be substantially fully covered, the number of installed pyrometers will be greatly reduced.
Whether scanning single-point temperature measurement or fixed multi-point temperature measurement is carried out, geometric reconstruction is needed to be carried out on a temperature measurement area to a certain extent, so that the temperature distribution of the surface of the measured blade is accurately obtained, and therefore, the research of a geometric surface reconstruction method of the turbine blade radiation temperature measurement area is very important.
Disclosure of Invention
The invention provides a geometrical surface reconstruction method of a radiation temperature measurement area of a turbine blade, which is based on Comsol Multiphysics multiple physical field simulation software and Matlab software, is favorable for realizing the geometrical surface reconstruction of the radiation temperature measurement area, and is particularly suitable for reconstructing the temperature field of the turbine blade.
The technical scheme of the invention is as follows:
the geometrical surface reconstruction method for the radiation temperature measurement area of the turbine blade is characterized by comprising the following steps of:
and step 5, processing the derived ray track data by Matlab data processing software, and reconstructing the geometric surface of the radiation temperature measurement area.
The step 1 includes: establishing three-dimensional space dimension, selecting a geometric optical physical field interface under a ray optical node, sequentially selecting addition and research, and finally selecting a selected physical field to preset ray tracing under a research node.
The configuration geometrical optical physical field in the step 3 comprises: modifying the geometric optics setting area 'maximum secondary ray number' to be 0; modifying a ray attribute setting area 'vacuum wavelength' under the geometrical optical node to a corresponding wavelength value; adding a wall attribute, wherein boundaries are selected as all boundaries, and wall conditions are set to be frozen; adding a 'ray detector attribute', and selecting a boundary as the surface of the measured blade; adding a 'release from boundary' attribute, selecting a boundary as a ray emission surface, selecting a 'grid-based' initial position, and checking 'specified tangential vector and normal vector components', and modifying the direction vector into a direction vector of an actually required ray emission direction; adding a specular reflection attribute according to actual conditions, and selecting a boundary as a reflecting surface; the configuration of the solver includes adding a "parametric scan", researching rotational angle parameters defined by parameter nodes selected as parameters in the setting, and inputting a list of parameter values, wherein the rotational angle parameters comprise an angular range of a leaf gap.
The step 4 includes modifying a "filter" under the ray tracing drawing set, changing the ray to be contained to a "logical expression" in the setting area, and corresponding the logical expression to the ray detector.
The data processing in the step 5 comprises the following steps:
step 5a, defining the temperature measurement target point number n and the angle data theta consistent with the parameter list i I=1, 2, …, m, i is a temperature measurement target sequence number, n is a positive integer, and m is a positive integer;
step 5b, loading the derived track data and extracting the tail ends of the tracks under different angles thetaThree-dimensional coordinates (x) j ,y j ,z j ) Where j=1, 2, …, n;
step 5c, extracting three-dimensional coordinates (x j ,y j ,z j ) Coordinate transformation under the space coordinate system is performed to obtain transformed three-dimensional coordinates (x k ,y k ,z k )，k＝1,2,…,n×m；
And 5d, performing geometric reconstruction and mapping corresponding radiation temperature values.
The invention has the following technical effects: the invention discloses a geometric surface reconstruction method of a radiation temperature measurement area of a turbine blade, which is beneficial to realizing three-dimensional visualization of radiation temperature measurement data. The specific embodiment comprises the following steps: configuring Comsol Multiphysics software environment; constructing a geometric model of the turbine blade to be tested, and carrying out grid division; configuring a geometrical optics physical field according to simulation conditions, and configuring a solver to solve and calculate; post-processing the result to obtain ray track data under the corresponding rotation angle; and processing the derived data by adopting data processing software such as Matlab and the like, and reconstructing the geometric surface of the radiation temperature measurement region.
Compared with the prior art, the invention has the advantages that: 1. according to the geometric surface reconstruction method for the turbine blade radiation temperature measurement region, when the high-temperature radiometer measures the temperature of the turbine blade in operation, the scanned temperature measurement region can be geometrically reconstructed, and the subsequent temperature block splicing process is simplified. 2. The geometric surface reconstruction method for the radiation temperature measurement area of the turbine blade is accurate and efficient in analysis process by means of finite element software, and has no complex equipment and structure. 3. According to the geometric surface reconstruction method for the radiation temperature measurement area of the turbine blade, the adopted geometric model is close to the actual working condition, the simulation of partial turbine blades is allowed except for the whole turbine disc, the calculation time can be greatly reduced, and the result is more credible.
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FIG. 1 is a schematic flow chart of a method for reconstructing a geometric surface of a radiation temperature measurement region of a turbine blade according to the present invention. Step 1, configuration Comsol Multiphysics software environment (Comsol Multiphysics, multiple physical fields simulation software) is included in fig. 1; step 2, constructing a geometric model of the turbine blade to be tested, and carrying out grid division; step 3, configuring a geometrical optics physical field according to simulation conditions, and configuring a solver to carry out solving calculation; step 4, post-processing the result to obtain ray track data under the corresponding rotation angle; and 5, processing the derived data (mathematical software manufactured by MathWorks company of the United states) by adopting data processing software such as Matlab and the like, and reconstructing the geometric surface of the radiation temperature measurement area.
FIG. 2 is a schematic view of a geometric model of a turbine blade in accordance with a referenceable embodiment of the invention.
Fig. 3 is a diagram of the effect of geometric reconstruction according to a reference embodiment of the present invention.
The reference numerals are explained as follows: 1-a measured leaf; 2-guide vanes; 3-adjacent vanes; 4-ray emission surface; 5-reflecting surface.
Detailed Description
The invention is described below with reference to the figures (fig. 1-3) and examples.
FIG. 1 is a schematic flow chart of a method for reconstructing a geometric surface of a radiation temperature measurement region of a turbine blade according to the present invention. FIG. 2 is a schematic view of a geometric model of a turbine blade in accordance with a referenceable embodiment of the invention. Fig. 3 is a diagram of the effect of geometric reconstruction according to a reference embodiment of the present invention. Referring to fig. 1 to 3, a geometric surface reconstruction method of a radiation temperature measurement region of a turbine blade is based on Comsol Multiphysics simulation software, and belongs to the technical field of radiation temperature measurement of the turbine blade. The method comprises the steps of configuring a simulation environment, importing a geometric model, configuring a geometric optical physical field interface, dividing grids, configuring a solver, calculating, then deriving ray track coordinates, carrying out transformation under a space rectangular coordinate system on the three-dimensional coordinates by Matlab, and finally carrying out geometric reconstruction and mapping corresponding radiation temperature values, thereby being beneficial to realizing geometric surface reconstruction of a radiation temperature measurement area and being particularly suitable for temperature field reconstruction of turbine blades.
The invention provides a geometric surface reconstruction method of a turbine blade radiation temperature measurement region, which is particularly suitable for reconstructing a temperature field of a turbine blade.
A geometric surface reconstruction method of a radiation temperature measurement area of a turbine blade is shown in fig. 1, and comprises the following steps:
step L1, configuring Comsol Multiphysics software environment;
step L2, constructing a geometric model of the turbine blade to be tested, and carrying out grid division;
step L3, configuring a geometrical optics physical field according to simulation conditions, and configuring a solver to carry out solving calculation;
step L4, post-processing the result to obtain ray track data under the corresponding rotation angle;
and step L5, processing the derived data by adopting data processing software such as Matlab and the like, and reconstructing the geometric surface of the radiation temperature measurement region.
In the following, a turbine blade including a tested blade and two adjacent guide vanes is described in detail, the geometric model is shown in fig. 2, and has 5 temperature measurement targets, so as to reconstruct the geometric surface of the temperature measurement region.
In the embodiment of the present invention, step L1 includes, but is not limited to: establishing three-dimensional space dimension, selecting a geometric optical physical field interface under a ray optical node, sequentially selecting addition and research, and finally selecting a selected physical field to preset ray tracing under a research node.
In the embodiment of the invention, the step L2 comprises inputting one or more standby parameters under the parameter nodes, so as to restrict the geometric relationship and facilitate the parameter scanning research, preferably the angle parameter theta; the geometric model comprises a measured movable blade 1, a guide blade 2, an adjacent guide blade 3, a radiation emitting surface 4 and a reflecting surface 5, wherein the geometric relation of the measured movable blade is relatively fixed; the geometric model adds rotation operation, an input object selects a movable blade 1 and a designated rotation shaft as the rotation shaft direction of the turbine disk, or selects a reflecting surface 4 and the designated rotation shaft as the rotation shaft direction of the reflecting surface 4 according to research requirements, and respectively inputs an angle parameter theta defined by a parameter node at an angle; the grid division method is preferably mapping, and divides the ray emitting surface and the reflecting surface into 5 uniformly distributed rectangular grids.
In an embodiment of the present invention, the configuration of the geometrical-optical-physical field in the step L3 includes, but is not limited to: modifying the geometric optics setting area 'maximum secondary ray number' to be 0; modifying the vacuum wavelength of the ray attribute setting area under the geometrical optical node to 1550nm; adding a wall attribute, wherein boundaries are selected as all boundaries, and wall conditions are set to be frozen; adding a 'ray detector attribute', and selecting a boundary as a pressure surface of the measured blade 1; adding a "release from boundary" attribute, selecting a boundary as a ray emitting surface, selecting an initial position "grid-based", wherein a refinement factor is preferably 1, and selecting "specified tangential vector and normal vector components", and modifying a direction vector to be (0, 1); with the addition of the "specular reflection" attribute, the boundary is chosen to be the reflecting surface 5. The configuration of the solver includes, but is not limited to, adding a "parametric scan", the choice of parameters in the study setting being the rotation angle parameter θ defined by the parameter node, and inputting a list of parameter values, preferably 2 °, with a scan interval of 0.5 °.
In an embodiment of the present invention, step L4 includes, but is not limited to, modifying a "filter" under the ray tracing drawing set, changing the rays to be included in the setting area to a "logical expression", and corresponding the logical expression to the ray detector.
In the embodiment of the present invention, the data processing step in step L5 includes:
(1) Defining the number of temperature measurement target points and angle data theta consistent with the parameter list i (i＝1,2,…,5)；
(2) Load the derived trajectory data and extract the three-dimensional coordinates (x) of the trajectory end at different angles θ j ,y j ,z j ) Where j=1, 2, …,5;
(3) Extracting three-dimensional coordinates (x j ,y j ,z j ) (j=1, 2, …, 25) performing coordinate transformation in a spatial coordinate system;
(4) Geometric reconstruction is performed and corresponding radiation temperature values are mapped, and the effect is shown in fig. 3.
What is not described in detail in the present specification belongs to the prior art known to those skilled in the art. It is noted that the above description is helpful for a person skilled in the art to understand the present invention, but does not limit the scope of the present invention. Any and all such equivalent substitutions, modifications and/or deletions as may be made without departing from the spirit and scope of the invention.
Claims (6)
1. The geometrical surface reconstruction method for the radiation temperature measurement area of the turbine blade is characterized by comprising the following steps of:
step 1, configuring Comsol Multiphysics software environment;
step 2, constructing a geometric model of the turbine blade to be tested, and carrying out grid division;
step 3, configuring a geometrical optics physical field according to simulation conditions, and configuring a solver and carrying out solving calculation to obtain a simulation result;
step 4, post-processing the result to obtain ray track data under the corresponding rotation angle;
and step 5, processing the derived ray track data by Matlab data processing software, and reconstructing the geometric surface of the radiation temperature measurement area.
2. The method for reconstructing a geometric surface of a radiation thermometry region of a turbine blade according to claim 1, wherein step 1 comprises: establishing three-dimensional space dimension, selecting a geometric optical physical field interface under a ray optical node, sequentially selecting addition and research, and finally selecting a selected physical field to preset ray tracing under a research node.
3. The method for reconstructing a geometric surface of a radiation thermometry region of a turbine blade according to claim 1, wherein step 2 comprises inputting one or more standby parameters under a parameter node of the turbine blade under test, thereby constraining the geometric relationship and facilitating a parameter scan study; the geometric model comprises a turbine disc or a blade, a ray emitting surface and a reflecting surface, wherein the position relation of the blade, the ray emitting surface and the reflecting surface is relatively fixed; the geometric model adds rotation operation, an input object selects a movable blade and designates a rotation shaft as the rotation shaft direction of the turbine disk, or selects a reflection surface and designates the rotation shaft as the rotation shaft direction of the reflection surface according to research requirements, and angle parameters defined by parameter nodes are respectively input at 'angles'; the grid division comprises dividing the ray emitting surface and the reflecting surface into grid numbers with the number corresponding to the temperature measuring target points.
4. The method for reconstructing a geometric surface of a radiation thermometry region of a turbine blade according to claim 1, wherein the configuring the geometric optical physical field in step 3 comprises: modifying the geometric optics setting area 'maximum secondary ray number' to be 0; modifying a ray attribute setting area 'vacuum wavelength' under the geometrical optical node to a corresponding wavelength value; adding a wall attribute, wherein boundaries are selected as all boundaries, and wall conditions are set to be frozen; adding a 'ray detector attribute', and selecting a boundary as the surface of the measured blade; adding a 'release from boundary' attribute, selecting a boundary as a ray emission surface, selecting a 'grid-based' initial position, and checking 'specified tangential vector and normal vector components', and modifying the direction vector into a direction vector of an actually required ray emission direction; adding a specular reflection attribute according to actual conditions, and selecting a boundary as a reflecting surface; the configuration of the solver includes adding a "parametric scan", researching rotational angle parameters defined by parameter nodes selected as parameters in the setting, and inputting a list of parameter values, wherein the rotational angle parameters comprise an angular range of a leaf gap.
5. The method of reconstructing a geometric surface of a radiation thermometry region of a turbine blade according to claim 1, wherein step 4 includes modifying a "filter" under the ray tracing map set, changing the rays to be included in the set region to a "logical expression", and associating the logical expression with the ray detector.
6. The method for reconstructing a geometric surface of a radiation thermometry region of a turbine blade according to claim 1, wherein the data processing in step 5 comprises the steps of:
step 5a, defining the temperature measurement target point number n and the angle data theta consistent with the parameter list i I=1, 2, …, m, i is a temperature measurement target sequence number, n is a positive integer, and m is a positive integer;
step (a)5b, loading the derived track data and extracting the three-dimensional coordinates (x) of the tail end of the track at different angles theta j ,y j ,z j ) Where j=1, 2, …, n;
step 5c, extracting three-dimensional coordinates (x j ,y j ,z j ) Coordinate transformation under the space coordinate system is performed to obtain transformed three-dimensional coordinates (x k ,y k ,z k )，k＝1,2,…,n×m；
And 5d, performing geometric reconstruction and mapping corresponding radiation temperature values.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116502469A (en) * | 2023-06-25 | 2023-07-28 | 中国航发四川燃气涡轮研究院 | Turbine blade temperature correction method and device based on temperature test data |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116502469A (en) * | 2023-06-25 | 2023-07-28 | 中国航发四川燃气涡轮研究院 | Turbine blade temperature correction method and device based on temperature test data |
| CN116502469B (en) * | 2023-06-25 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Turbine blade temperature correction method and device based on temperature test data |
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